DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0578; Directorate Identifier 2013-SW-048-AD;
Amendment 39-18684; AD 2016-21-03]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters Deutschland GmbH
(Previously Eurocopter Deutschland GmbH) (Airbus Helicopters)
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus
Helicopters Model MBB-BK 117 C-2 helicopters with certain duplex trim
actuators installed. This AD requires repetitively inspecting the
lateral and longitudinal trim actuator output levers for correct torque
of the nuts. This AD was prompted by a design review that indicated the
attachment screws can become loose under certain circumstances. These
actions are intended to prevent the loss of an attachment screw, which
could result in movement of the output lever in an axial direction,
contact of a bolt connecting the control rod to an output lever with
the actuator housing, and subsequent loss of helicopter control.

DATES: This AD is effective November 25, 2016.

ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie,
TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-
3775; or at http://www.airbushelicopters.com/techpub. You may review
the referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort
Worth, TX 76177.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov
or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the European Aviation Safety
Agency (EASA) AD, the economic evaluation, any comments received, and
other information. The street address for the Docket Operations Office
(phone: 800-647-5527) is U.S. Department of Transportation, Docket
Operations Office, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177; telephone
(817) 222-5110; email matt.wilbanks@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

On August 18, 2014, at 79 FR 48696, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 by adding an AD that would apply to Airbus Helicopters
Model MBB-BK 117 C-2 helicopters with a lateral duplex trim actuator,
part number (P/N) 418-00878-050 or P/N 418-00878-051, or a longitudinal
duplex trim actuator, P/N 418-00878-000 or P/N 418-00878-001,
installed. The NPRM proposed to require repetitively inspecting the
lateral and longitudinal trim actuator output levers for correct torque
of the nuts. The proposed requirements were intended to prevent a loose
attachment screw, which could result in movement of the output lever in
an axial direction, contact of a bolt connecting the control rod to an
output lever with the actuator housing, and subsequent loss of
helicopter control.
The NPRM was prompted by AD No. 2013-0182, dated August 12, 2013,
issued by EASA, which is the Technical Agent for the Member States of
the European Union, to correct an unsafe condition for Airbus
Helicopters Model MBB-BK 117 C-2 helicopters with a lateral duplex trim
actuator, P/N 418-00878-050 or P/N 418-00878-051, or with a
longitudinal duplex trim actuator, P/N 418-00878-000 or P/N 418-00878-
001. EASA advises that under unfavorable circumstances, a total loss of
the trim actuator output lever attachment screw could lead to a
restriction of the lateral and longitudinal control range. According to
EASA, without the attachment screw, the output lever can move in the
axial direction. This condition, if not detected, could cause the bolt
that connects the control rod to the output lever to make contact with
actuator housing, possibly resulting in reduced control of the
helicopter.
To prevent this condition, EASA requires an initial torque check of
the lateral and longitudinal trim actuator output lever attachment
screws, the application of a torque marking, and repetitive inspections
for correct torque thereafter. The EASA AD's requirements are
considered an interim solution, pending a terminating modification.
Since the issuance of EASA AD No. 2013-0182, Eurocopter Deutschland
GmbH has changed its name to Airbus Helicopters Deutschland GmbH.

Comments

We gave the public the opportunity to participate in developing
this AD, but we received no comments on the NPRM (79 FR 48696, August
18, 2014).

FAA's Determination

These helicopters have been approved by the aviation authority of
Germany and are approved for operation in the United States. Pursuant
to our bilateral agreement with Germany, EASA, its technical
representative, has notified us of the unsafe condition described in
the EASA AD. We are issuing this AD because we evaluated all
information provided by EASA and determined the unsafe condition exists
and is likely to exist or develop on other helicopters of these same
type designs and that air safety and the public interest require
adopting the AD requirements as proposed.

Interim Action

We consider this AD to be an interim action because Airbus
Helicopters is currently developing a modification that will address
the unsafe condition identified in this AD. Once this modification is
developed, approved and available, we might consider additional
rulemaking.

Related Service Information

We reviewed Eurocopter (now Airbus Helicopters) Alert Service
Bulletin MBB-BK117 C-2-67A-020, Revision 0, dated June 18, 2013 (ASB),
which advises of a design review that showed that a loss of the
attachment screw of the trim actuator output lever could restrict the
lateral and longitudinal control range. The ASB consequently calls for
an initial torque check and application of torque markings of the self-
locking nuts, and subsequent repetitive inspections to maintain the
proper torque.

Costs of Compliance

We estimate that this AD affects 100 helicopters of U.S. Registry
and that labor costs average $85 per work-hour. Based on these
estimates, we expect the following costs:
Applying torque and torque marking to the lateral and
longitudinal trim actuator output levers requires 1 work-hour for a
labor cost of $85. No parts are needed, so the cost for the U.S. fleet
totals $8,500.
Visually inspecting for correct torque requires 0.5 work-
hour for a labor cost of about $43. No parts are needed, so the total
cost for the U.S. fleet is $4,300 per inspection cycle.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on helicopters identified in this
rulemaking action.

Regulatory Findings

This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction; and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):